Zero gravity separator



June 28, 1966 Filed Oct. 18, 1963 JAMES E. WEBB ADMINISTRATOR OF THENATIONAL AERONAUTICS AND SPACE ADMINISTRATION ZERO GRAVITY SEPARATOR 5Sheets-Sheet l ALEXANDER 12. Ros/N A Max-02o Po e l INVENTORS fzmx'fl;7% KW ATTORNEYS June 28, 1966 JAMES E. WEBB 3,257,780

ADMINISTRATQR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ZEROGRAVITY SEPARATOR Filed Oct. 18, 1963 5 Sheets-Sheet 2 47 77 8| 7& 7s a00 z l 5Z4 2 VENTORS 11.1.5 xn/vosi? .D R osnv A MILFORD POPE ATTORNEYSJune 28, 1966 JAMES E. WEBB ADMINISTRATOR OF THE NATIONAL AERONAUTICSAND SPACE ADMINISTRATION ZERO GRAVITY SEPARA'IOR M 5 m a n w 8 APV a. bm r m 22 0 e E0 6 DP w NH. W A 5 W A w Filed Oct. 18, 1963 ATTOEN EYSJune 28, 1966 JAMES E. WEBB 3,257,780

ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ZEROGRAVITY SEPARATOR Filed Oct. 18, 1963 5 Sheets-Sheet 4 ALEXHNDEE D-ROS/N POPE MLFOED INVENTORS AT T'OIZNEYS June 28, 1966 JAMES E. WEBBADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ZEROGRAVITY SEPARATOR Filed Oct. 18, 1963 5 Sheets-Sheet 5 gee yzmL

IN VEN TO OSIN P PE I AITo ENEVS United States Patent 3,257,780 ZEROGRAVITY SEPARATOR James E. Webb, Administrator of the NationalAeronautics and Space Administrationwith respect to an invention ofAlexander D. Rosin and A. Milford Pope Filed Oct. 18, 1963, Ser. No.317,391 14 Claims. (Cl. 55160) The present invention relates generallyto apparatus for separating mixtures of gases and liquids from eachother, and is more particularly directed to apparatus for separating gasfrom a liquid in which the gas is suspended under zero gravityconditions, and thereafter venting the gas while retaining the liquid.

In various applications it is necessary to separate mixtures of gasesand liquids. For example, it is frequently desirable to separate liquidpetroleum from gas products suspended therein or to separate theconstituents of a fluid in a double-phase condition, i.e., gasesentrained in a liquid. The latter application of liquid and gasseparation has recently become of particular importance in the conductof various space missions. More particularly, under conditions ofweightlessness, or zero gravity, as experienced by space vehicles duringvarious missions, cryogenic materials, such as liquid hydrogen containedin the fuel tank of the vehicle, absorb heat energy through radiationfrom the earth and sun, and this influx of heat energy raises thetemperature of the cryogenic material sufficiently to cause boil-off.Due to the weightlessness, the gas generated due to boil-off remainssuspended in the liquid and, accordingly, a double-phase fluid iscontained within the tank. Inasmuch as the gas generated from boil-offresults in increased tank pressure, it is necessary to vent the tankpressure to a safe minimum. In order -to vent the tank pressure withoutventing liquid, it is, of

course, necessary to separate the gas from the liquid and vent the gaswhile returning the liquid to the tank.

It is, therefore, an object of the present invention to provide agas-liquid separator having particular application in the venting ofpressure of a space vehicle fuel tank containing cryogenic materialwhich exists as a double-phase fluid under zero gravity conditions.

Another object of the invention is to provide gas-liquid separation andgas venting apparatus for employment in a region containing double-phasefluid, which apparatus is so arranged that the gas, prior to beingvented, extracts heat from the liquid returned to the containment regionto reduce the tendency of the liquid to convert to the double-phasecondition.

Still another object of the invention is the provision of separation andventing apparatus of the class described which is operable in responseto pressures in the region containing the double-phase fluid in excessof a predetermined safe minimum pressure, while being inoperable inresponse to pressures in the region less than the predetermined minimum.

It is yet another object of the invention to provide apparatus of theclass described which includes control means for selectively activatingor inactivating the apparatus such that the apparatus may be normallymaintained in an inactive state while being activated for pressureresponsive operation only when certain external conditions prevail, suchas when a space vehicle is in a particular attitude.

Another object of the invention is to provide liquid-gas separating and'gas venting apparatus wherein moving parts are cooled by the separatedgas prior to venting thereof.

It is a further object of the invention to provide separator apparatusof the class described which may be readily arranged to have a minimumof angular momentum dur ing its operation.

3,257,780 Patented June 28, 1966 "ice A still further object of theinvention is to provide zero gravity liquid-gas separating and gasventing apparatus which requires substantially no external power in itsoperation.

Additional objects and advantages of the invention will become apparentupon consideration of the following description taken in conjunctionwith the accompanying drawings, wherein:

FIGURE 1 is a schematic illustration of a space vehicle fuel tankequipped with liquid-gas separating and gas venting apparatus inaccordance with the present invention in the upper regions thereof,cryogenic material contained within the tank being depicted as travelingupwardly into the region of the separator under zero gravity condition;

FIGURE 2 is a schematic illustration of one form of the invention;

FIGURES 3-5, inclusive, are schematic illustrations of a valvearrangement employed in the embodiment of FIGURE 2 under variedoperating conditions;

FIGURE 6 is a fragmentary sectional view taken at line 66 of FIGURE 2,illustrating the vane arrangement of a heat exchanger of the apparatus;

FIGURE 7 is a schematic illustration of a modified form of theinvention;

1 FIGURE 8 is a sectional view taken at line 88 of FIGURE 7,illustrating particularly the heat exchanger of the modified apparatus;

FIGURE 9 is a schematic illustration of the apparatus of FIGURE 7 asrotated FIGURES 10 and 11 are similar fragmentary views on an enlargedscale schematically illustrating a control valve of the apparatusillustrated in FIGURES 7-9 under varied operating conditions; and

FIGURES 12 and 13 are similar fragmentary views on an enlarged scaleschematically illustrating a pilot valve of the apparatus of FIGURES 7-9in varied conditions of operation.

Referring now to FIGURE 1 of the drawing, the invention will be seen tobe illustrated with respect to a space vehicle fuel tank 11 containing acryogenic material, such as liquid hydrogen, as generally indicated at12. It is assumed that boil-off of the cryogenic material has occurredsuch that gas also exists within the tank 11. Moreover, the tank issubjected to zero gravity conditions such that the material exhibitsWeightlessness and travels upwardly in the fuel tank. As a result, thegas generated by boil-off is entrained in the liquid and, accordingly,provides a double-phase fluid, as indicated at 13, in the upper regionsof the tank. In order to accomplish separation of the gas from theliquid and to vent the gas from the tank without venting liquid so as tomaintain the tank pressure at a safe minimum, gas-liquid separating andgas venting apparatus 14, in accordance with the present invention, islocated in the upper regions of the fuel tank 11. In this regard, theapparatus 14 may be advantageously associated with or attached to thefuel tank manhole or cover plate 16, so as to be suspended therefrominto the upper regions of the tank. The doublephase fluid 13 thus entersthe apparatus 14 and, by means outlined hereinafter, is separated intoliquid and gas, the liquid being returned to the tank, while the gas isvented therefrom. Although the apparatus of the invention isparticularly described with reference to space vehicle fuel tanks underzero gravity conditions, it will become apparent that the apparatus maybe advantageous employed in a comparable manner in various otherequivalent environments.

Considering now the apparatus 14, mentioned above with respect to FIGURE1, as to its basic aspects with reference to the several forms thereofillustrated particularly in FIGURES 2 and 7, respectively, it will benoted 3 that the apparatus includes separator means which are adaptedfor communication with a region containing a gas and liquid mixture, forexample, the upper portions of the fuel tank 11 under conditions of zerogravity. The separator means includes a member which is mounted fordriven movement and is positioned to intercept the liquidgas mixture.This member in its movement propels the liquid of the mixture throughliquid flow passages of a heat exchanger disposed adjacent the separatormember. The separator member is further arranged to channel the gas ofthe mixture to an expansion motor, such as a turbine, which is coupledin driving relation to the separator member to effect the movementthereof. The gas expands in motivating the expansion motor and isconsequently cooled to a considerable extent. The apparatus furtherincludes means for receiving the expanded gas from the expansion motorand conveying same to gas passages of the heat exchanger which are inheat exchange relation with the liquid passages thereof. During the flowof gas through the gas passages of the heat xchanger, the

liquid is hence thereby cooled in passing through the liquid passagesfor return to the tank, or other region containing the double-phasefluid. A vent is provided which is adapted for disposition exteriorly ofthe region containing the gas and liquid mixture. For example, the vent'may extend through the cover plate 16 of the fuel tank 11. The gaspassages of the heat exchanger are communicated with the vent, andsubsequent to passage of the gas through the heat exchanger, the gas isported through the vent exteriorly of the region containing the gas andliquid mixture. It will be appreciated that aside from accomplishingventing of the pressure of a region containing a gas and liquid mixtureto a safe minimum while retaining the liquid in the region, theapparatus provides the added advantage of cooling the liquid to reducethe tendency thereof to convert to the double-phase condition. Theapparatus may also be advantageously provided with pressure sensitiverelief valve means in the flow path from the separator member to theexpansion motor to control the flow of gas thereto in response to theabsolute pressure existing in the tank 11, or other containment region.More particularly, the valve means may be arranged to preventcommunication with the expansion motor responsive to tank pressures lessthan a predetermined minimum safe level, and to establish communicationto the expansion motor in response to pressures equal to or greater thanthe predetermined minimum safe level. The valve means thus is operableto activate the separator and venting apparatus when the tank pressurebecomes excessive to thereby relieve the pressure, while inactivatingthe apparatus when the tank pressure is tolerable. The valve means mayfurther advantageously include control valve means for selectivelyswitching the apparatus between an active state of pressure responsiveoperation, and an inactive state wherein the apparatus is inoperableirrespective of the pressure existing in the tank. The control valvemeans may be arranged, for example, to activate the apparatus forpressure sensitive operation only when the space vehicle is in aparticular attitude, or when certain other predetermined conditionsexist.

Considering now the separator and venting apparatus generally outlinedabove in greater detail as to a particular embodiment thereof andreferring to FIGUREZ, there will be seen to be provided a double-endedarrangement wherein components of the opposit ends thereofcounterrotatae in order to reduce angular momentum of the overallapparatus to negligible level. Inasmuch as both ends of the double-endedarrangement are identical, only one end is hereafter described in detailwith the like components of the other end being identified by likeprimed reference numerals. More particularly, the left end, as viewed inFIGURE 2, of the double-ended separator and venting apparatus includes acircular separator disc 17, which serves as the separating member ofprevious mention, and is concentrically disposed within an annular heatexchanger 18. More particularly, the disc 17 is coaxially secured to ashaft 19 which is journaled for rotation between an end of the heatexchanger and a turbine housing 21 coaxially aligned with the heatexchanger. In this regard, a journal bearing 22 may be supportedcentrally of the annular heat exchanger 18, as by means of a spider, orthe like (not shown), to provide an end mounting for the shaft 19 whileyet enabling fluid to enter the central opening of the heat exchangerfor separating action by the disc 17. More particularly, the disc 17 isprovided with a plurality of radially extending gas inlets 23 interminal communication with a gas flow passage 24 which extendslongitudinally through the shaft 19. Thus, gas entering the centralopenings of the heat exchanger 18 from a region containing a mixture ofgas and liquid flows into the gas inlets 23 of the disc 17 to thelongitudinal flow path 24 of the shaft 19. When the disc is rotating,liquid entering the central opening of the heat exchanger 18 strikes therotating disc and is thrown or propelled radially outward to thesurrounding heat exchanger. As shown in FIGURE 6, the heat exchangerincludes a plurality of circumferentially spaced radial vanes 26defining a plurality of radial liquid passages 27 through the heatexchanger. Liquid propelled outwardly by the rotating disc consequentlypasses through the passages 27 and is returned to the tank or otherregion containing the gas and liquid mixture. It will be thusappreciated that the separator disc 17 in its rotation is operable toseparate the gas from the liquid of the mixture and to direct the liquidthrough the heat exchanger 18 with beneficial results subsequentlydescribed herein.

The turbine housing 21 is provided with a central chamber 28 centrallyof which a bearing 29 is mounted to journal the corresponding end ofshaft 19. A turbine 31 disposed in the chamber 28 is coaxially securedto the shaft 19 so as to be rotatable therewith, and it will be thusappreciated that the turbine comprises the expansion motor means of theseparator and gas venting apparatus. In order to convey the separatedgas from the flow passage 24 of the shaft 19 into motivating relation tothe turbine 31, the housing 21 is provided with a radial flow passage 32which is in sealed relation to the shaft 19 while permitting rotationthereof and communicates with radial outlets 33 which extend from theflow passage 24. The passage 32 is communicated with the chamber 28,preferably through a relief valve 34 which is subsequently described indetail herein and which is secured to the turbine housing 21. Gasdelivered from the valve 34 is preferably fed to a nozzle box 36, or thelike, disposed in the housing 28 in a position to direct the gas uponthe vanes of the turbine 31, in driving relation thereto. Thus, withflow established through the relief valve from the flow passage 24 ofthe shaft 19, the gas drives the turbine 31, which in turn drives theshaft 19 and separator disc 17 secured thereto. Similarly, gas enteringthe other end of the apparatus is directed through the gas inlets 23 ofthe separator disc 17 to the longitudinal flow passage 24' of shaft 19,and is channeled through relief valve 34 to th nozzle box 36', which islocated in the chamber 28 on the opposite side thereof from nozzle box36 at a position diametrically opposed thereto. The gas directed fromthe nozzle box 36 upon the vanes of the turbine 31' effects rotationthereof, which in turn rotates the shaft 19' and the separator disc 17connected thereto. The vanes of turbine 31 ar oppositely pitched fromthe vanes of turbine 31 such that the gas streams directed from nozzleboxes 36 and 36 cause the turbines to rotate in mutually oppositedirections. The gas directed from the nozzle boxes expands and is cooledto some extent in driving the respective turbines but still retains asignificant quantity of energy.

' mediate the turbines 31' and 31'.

In order that the residual energy of the gas streams subsequent todriving the turbines 31 and 31 be effectively utilized and the gas befurther expanded and cooled, means are preferably providedto channeleach of the gas streams, subsequent to its driving one turbine, intomotivating relation with the other turbine such that the residual energyof the .gas stream contributes to the rotation thereof. Moreparticularly, orifices 37 and 37 are advantageously mounted with thechamber 28, as by means of a spider 38, at a position longitudinallyinter- The longitudinal passages of the orifices 37 and 37' arerespectively aligned with the outlets of the nozzle boxes 36 and 36'.Orifice 37 thus receives the gas directed from nozzle box 36 subsequentto its driving of the turbine 31 and channels the gas into drivingrelation to turbine 31' to thus contribute to the rotation thereof inthe opposite direction, the vanes of this turbine being oppositelypitched as previously noted. Similarly, the gas stream directed fromnozzle box 36' is received by orifice 37 subsequent to its driving ofthe turbine 31', and is channeled through the orifice into drivingrelation to the turbine 31 to contribute to the rotation thereof. Itshould also be noted, as an important adjunct of the invention, that gasflow passages 39 and 39' are communicated with the orifices 37 and 37and extend into the bearings 29 and 29. Portions of the gas streamsflowing through the orifices are thus conveyed to the hearings toeflfect cooling thereof.

Subsequent to driving both turbines 31 and 31, the gas streams directedfrom the nozzle boxes 36 and 36', as expanded and cooled to aconsiderable extent, are directed through the heat exchangers 18' and18, respectively, to effect cooling of the liquid propelledtherethrough. More particularly, channels 41 are provided longitudinallyof each heat exchanger to define gas flow passages 42 longitudinallytherethrough. Flow paths 43 and 43' communicating with the chamber 28 atpositions adjacent turbine 31 and orifice 37' and adjacent turbine 31'and orifice 37 then serve to convey the expanded cool gas to the gasflow passages 42 of the respective heat exchangers 18 and 18. Inasmuchas the gas is quite cool, substantial heat is extracted from the liquidpropelled outwardly through the liquid flow passages 26 of the heatexchangers for return to the tank 11, or equivalent region containinggas and liquid mixture. By virtue of the cooling of the liquid returnedto the tank, the tendency of p the liquid to convert to the double-phasecondition is significantly reduced.

In order that the gas flowing through the heat exchangers 18 and 13' maybe ported exteriorly of the tank, or other region containing gas andliquid mixture, an outlet vent 44 is disposed exteriorly of the region.The gas passages of the heat exchangers are in turn communicated withthe vent 44 by means including outlet flow paths 46 and 46 whichcommunicate with the vent 44, in the present instance through a controlvalve 47. The control valve is operatively associated with the reliefvalves 34 and 34 in such a manner that in an activating state of thecontrol valve, gas flow to the turbines 31 and 31, and hence operationof the over-all apparatus, is controlled by the pressure Within the tankor other region containing the gas and liquid mixture. The control valve47 is further arranged such that in an inactive state of the valve, theover-all apparatus is rendered inoperable irrespective of the pressureexisting in the region of the mixture.

Considering now the valving arrangement employed in the embodiment ofFIGURE 2 in greater detail, it will be noted that the relief valves 34and 34 respectively include valve bodies 48 and 48' having chambers 49and 49' therein. The valve bodies further include inlet ports 51 and 51'which communicate the flow passages 32 and 32' with the chambers 49 and49. In addition, outlet ports 52 and 52 in the valve bodies communicatethe chambers 49 and 49' with the nozzle boxes 36 and 36' 6 disposed inthe turbine chamber 28. The outlet ports 52 and 52 respectively includeseats 53 and 53' which are engageable by plug members 54 and 54' carriedby accordion members or bellows 56 and 56' respectively mounted withinthe relief valve chambers 49 and 49.

The bellows are expansively and contractively movable to respectivelyengage the plug members 54 and 54 with the seats 53 and 53', and todisengage the plug members therefrom, depending upon whether thepressure acting at the exterior of the bellows is less than, or greaterthan the pressure acting at the interior thereof. Thus, when thepressure of gas introduced to the relief valve chambers 49 and 49through the inlet ports 51 and 51 exceeds the pressure acting interiorlyof the bellows 56 and 56, the bellows contract to move the plug members54 and 54' out of engagement with the seats 53' and 53', therebyestablishing flow to the nozzle boxes 36 and 36'.

As a result, the turbines 31 and 31' are driven to, in turn,

drive the shaft and separator discs 17 and 17', i.e., the apparatus isrendered operable to conduct its separating and gas venting functions.Conversely, when the gas pressure in the relief valve chambers 49 and 49is less than the pressure acting interiorly of the bellows 56 and 56',the latter expansively move the plug members 54 47 which is arranged toappropriately control the pressures at the interiors of the bellows inaccordance with the pressure existing in the tank, or other regioncontaining the gas-liquid mixture. More particularly, the control valve47 includes a valve body 57 having a pilot control port 58 communicatedby flow paths 59 and 59 with the interiors of the relief valve bellows56 and 56'. The

control port 58 communicates with a pilot chamber 61 provided in thecontrol valve body 57 and this chamber is communicated by means of aleak 62 with a control pressure chamber 63. An accordion member 64 ismounted in the chamber 63 and a stem 66 extends therefrom into the pilotchamber 61, a dynamic seal being provided between the stern and chambersas by means of a bellows 67. A valve member 68 is carried at the end ofthe stem 66 in the pilot chamber 61 for engagement with a seat 69therein defining the entrance to an outlet passage 71 therefrom. Inaddition, an inlet port 72 communicates with the control pressurechamber 63 which is adapted for communicable connection with the tank orother region containing the gas and liquid mixture. Thus, the tankpressure is transmitted to the control pressure chamber 63 via the inletport 72. Moreover, the acseat 69 to thus close the outlet passage 71.When the tank pressure as transmitted by the inlet port 72 to thecontrol pressure chamber 63 is equal to or exceeds the predeterminedsafe minimum level, the accordion member 64 contracts to therebydisengage the valve member 68 from the seat 69 and open the outletpassage 71. It is to be noted that the outlet passage 71 is communicatedwith the vent 44, which in the instance of a space vehicle undergoing aspace mission is disposed in a vacuum. Under other environmentalconditions, the vent is otherwise ported to a region having relativelylow pressure compared to that existing within the tank. Thus, when thevalve member 68 is disengaged from the seat 69 under conditions ofexcessive pressure in the tank as transmitted to the control pressurechamber 63, the pilot chamber 61, and therefore the interiors of therelief valve bellows 56 and 56' communicated therewith, are ventedthrough the outlet passage 71 and vent 44 to vacuum or other extremelylow pressure. Thus, the gas flowing into the relife valve chambers 49and 49 is at a substantially greater pressure than the pressure existinginteriorly of the bellows. Accordingly, communication is establishedthrough the relief valves 34 and 34 to the nozzle bOXes 36 and 36 fordriving the turbines. However, when the tank pressure as transmitted tothe control pressure chamber 63 is not excessive and the accordionmember 64 engages the valve member 68 with the seat 69 to close theoutlet passage 71, this tank pressure also exists within the pilotchamber 61 by virtue of the leak 62 between the control pressure chamberand the pilot chamber. Thus, tank pressure is at this time maintainedwithin the interiors of the relief valve bellows 56 and 56' and thispressure is greater than the gas pressure acting within the relief valvechambers on the exteriors of the bellows. The plug members 54 and 54'are consequently engaged with seats 53 and 53' to thus prevent the flowof gas to the turbine actuating nozzle boxes 36 and 36', thus renderingthe overall apparatus inoperable.

To facilitate selective switching of the apparatus between activepressure controlled, and inactive states, the control valve 47 includesa solenoid actuated piston 73 mounted for reciprocation within acylinder bore 74 provided in the control valve body 57. A stem 76projects coaxially from the piston 73 into an outlet chamber 77 througha communicating passage 78 having walls outwardly spaced from the stern.A seat 79 is provided in the outlet chamber 77 about the termination ofthe passage 78. A plug member 81 secured to the end of the stem 76 isengageable with the seat 79 in response to solenoid actuated movement ofthe piston 73, to the right as viewed in FIGURE 2. An inlet passage 82in communication with passage 78 is coupled to the outlet flow paths 46and 46' from the heat exchangers 18 and 18, while the outlet passage 71from pilot chamber 61 and the vent 44 are both communicated with theoutlet chamber 77. Solenoids 82 and 83 in association with the controlvalve body 57 are provided to effect movement of the piston 73 betweenactivating and inactivating positions wherein the valve member 81 isrespectively in engagement with, and disengaged from the seat 79, inresponse to appropriate energization of the solenoids. When the solenoidactuated piston 73 is in its active position with the valve member 81disengaged from the seat 79, as shown in FIGURE 2, the outlet chamber77, and therefore the vent 44, are communicated with the outlet flowpassages 46 and 46 from the heat exchangers through the inlet passage 82and passage 78. Thus, operation of the apparatus proceeds under thepressure sensitive control of the accordion member 64 in response to thepressure in the tank or other region containing the gas and liquidmixtures. When the solenoid actuated member 73 is in its inactiveposition, however, and the valve member 81 engages the seat 79.,communication is blocked between passage 78 and the outlet chamber 77.Therefore, even though the relief valves 34 and 34 are controlled toestablish gas flow to the turbine actuating nozzle boxes 36 and 36', theoutlet flow of gas from the heat exchangers is blocked from the vent 44and therefore gas flow through the over-all apparatus is prevented torender same inoperable.

From the foregoing, it will be appreciated that the control valve 47 mayassume four separate conditions of control of the separating and gasventing apparatus. More particularly, in one condition as depicted inFIGURE 2, the solenoid actuated valve means of the control valve is inactive venting position and the pilot valve means is opened due to anexcessive tank pressure sensed in the control pressure chamber 63. Inthis condition of the control valve 47, the relief valves 34 and 34' areresponsively opened to permit pressure relieving gas flow through theapparatus to the outlet port 44 in the manner hereinbefore described.

A second condition of the control valve is illustrated in FIGURE 3wherein the solenoid actuated valve means is in active venting position,but the pilot valve means is in closed inactivating position by virtueof the tank pressure sensed in the control pressure chamber 63 beingnonexcessive. As a result, the relief valves are responsively closed,and gas flow to the turbines is prevented to thereby render theapparatus inactive. However, inasmuch as the solenoid actuated valvemeans is in active venting position in this second condition, upon abuildup of tank pressure to an excessive level, the valve reverts to thefirst condition and gas is ported to the vent 44.

A third condition of the control valve is illustrated in FIGURE 4wherein the solenoid actuated valve means has been actuated to inactiveposition while the pilot valve means is likewise in closed, apparatusinactivating position due to the sensed tank pressure beingnonexcessive.

In the fourth condition of the valve, as illustrated in FIGURE 5, thepilot valve means is in open apparatus activating position due to anexcessive tank pressure and the relief valves are, accordingly, alsoopened. However, the solenoid actuated valve means is still in itsinactive position wherein the valve member 81 is in engagement with theseat 79 to block communication between the outlet chamber 77 and thepassage 78. Accordingly, despite the pilot valve being in apparatusactivating position, the apparatus is rendered inactive by virtue of thesolenoid actuated valve means preventing gas flow to the vent 44.

Considering now a single-ended embodiment of liquidgas separating andgas venting apparatus in accordance with the invention and which is alsosomewhat modified in further respects from the embodiment hereinbeforedescribed, reference is now made to FIGURE 7. As shown therein, theseparator member is provided as an elongated hollow shaft 86 which has aplurality of outwardly extending vanes 87 at longitudinally spaced positions thereof which encompass radial gas inlets 88 which extend throughthe shaft wall to its hollow interior 89. A perforated shroud or tube 91is mounted in concentric outwardly spaced relation to the shaft 86, anda bafile 92 is provided between the shaft and shroud at one end thereofwhile the other end is open to permit the inflow of gas and fluidmixture to the annulus between the shaft and shroud. The assembly ofshaft and shroud is concentrically disposed within a hollow elongatedcylindrical heat exchanger 93 comprising a nest of spaced longitudinallyextending tube 94 mounted in an annular array between end plates 96 and97. The tubes extend through the end plates, and a cap 98 is coaxiallysecured to the end plate 97 in such a manner as to define an annulus 99communicating the tubes 94 extending through this end plate. The shaft86 is journaled centrally of the cap 98 at one end while the other endof the shaft extends through, and is journaled centrally in the endplate 97. The shaft is closed at its end adjacent the cap 98 and the capincludes perforations as indicated at 101 to admit gas and liquid to theannulus between the shaft 86 and shroud 91. With the shaft in rotation,the liquid upon striking the vanes 87 is propelled outwardly through theshroud perforations and through'the spaces between the tubes 94 of theheat exchanger 93 to be thereby returned to a tank or the like withinwhich the apparatus is disposed. Entering gas flows around the vanes 87in the manner indicated by the serpentine-shaped arrows of FIGURE 7 andthrough the inlets 88 to the hollow shaft interior 89.

A turbine housing 102 is coaxially secured to the end plate 97 of theheat exhanger 93 and end openings 103 from the hollow interior 89 ofshaft 86 communicate with a chamber 104 in the turbine housing. Apassage 106 extends from. the chamber 104 to convey gas, introduced tothis chamber from the hollow shaft interior 89, to a relief valve 107,subsequently described in detail, where the gas is divided into twoportions. One

portion of the gas is conveyed from the relief valve to a first nozzle108 which extends into a turbine chamber 109 provided in the housing102. The other portion of gas from the relief valve is conveyed to asecond turbine nozzle 111 which extends into the turbine chamber 109 inopposed transversely offset relation to the nozzle 108 as best shown inFIGURE 9. Gas is directed from the nozzles upon the vanes of a turbine112 rotatably mount ed within the chamber 109, thereby effectingrotation of the turbine. In the rotatable mounting of the turbine, ashaft 113 is preferably journaled coaxially of the turbine chamber 109and extends through a chamber 114, interposed between the chamber 109and the chamber 104, and into the latter chamber. A suitable coupling116 then couples shaft 113 to hollow shaft 86. The turbine 112 includesan integral sleeve shaft 117 which is concentrically rotatably disposedupon the shaft 113 and extends into the chamber 114. A magnetic frictionclutch 118 disposed in chamber 114 is provided to couple the sleeveshaft 117 of theturbine to the shaft 113. The tubine 112 is thus coupledin driving relation to the hollow shaft 86 with the magnetic clutch 118providing increased acceleration characteristics of the turbine.

The gas directed from the turbine nozzles 108 and 111 is expanded andcooled in driving the turbine 112 and the hollow varied shaft 86 coupledthereto and the expanded cooled gas is channeled from the turbinecompartment 109 to a manifold chamber 119 provided in the housing 102 ata position of communication with the tubes 94 extending through the endplate 97 from a semi-circular half sector of the heat exchanger. Theexpanded cool gas thus flows through the tubes of this sector and at theopposite ends of these tubes into the annulus 99 which channels the gasto the ends of the tubes of the remaining semi-circular half sector ofthe heat exchanger. The opposite ends of the tubes of this latter sectorwhich extend through the end plate 97 communicate with a chamber 121provided in the housing 102. The gas is conveyed from this chamherthrough a plurality of inlets 122 which serve to communicate the chamber114 therewith. The chamber 114 is communicably coupled to an outlet vent123 by means of a shut-off valve 124, subsequently described in detailherein. Thus, the expanded cool gas from the turbine chamber 109 makes adual pass through the heat exchanger 93 to therein cool the liquidpropelled outwardly through the heat exchanger from'the vanes 87 of thehollow shaft 86. The gas is thereafter returned to the turbine housingand channeled through the chamber 114 to cool the magnetic clutch 118enroute to the vent 123.

Considering now the v-alving arrangement employed with the embodiment ofFIGURES 7-9, it is to be noted that the relief valve 107 includes a body126 having a chamber 127 communicated with the passage 106 for conveyingthe gas received in chamber 104 from the interior 89 of the shaft 86. Arecess 128 is provided in the body 126 which communicates with thechamber 127 and is provided with a valve seat 129 thereat. A pair ofoutlet ports 130 communicate with the recess 128 in order to divide thegas flow therefrom into the two portions which are respectively appliedto the turbine nozzles 108 and 111.

A bellows 131 is mounted within the. chamber 127 and carries a plug 132which is engageable with the seat 129 upon expansion of the bellows andis disengaged from the seat upon contraction of the bellows. As in theinstance of the relief valves 34 and 34' of the embodiment of FIGURE 2,expansion and contraction of the bellows 131 of relief valve 107 iscontrolled by the pressure differential between the gas acting on theexterior of the bellows and the pressure interiorly thereof. In theinstant embodiment, the interior pressure of the bellows 131 iscontrolled by means of a pilot valve 133 in a manner similar to thatdescribed with respect to the pilot valve means of the previousembodiment.

The pilot valve 133, as will be best seen from FIG- URES 9, and 12 and13, is arranged to apply tank pressure to the interior of the reliefvalve bellows 131 when the tank pressure is less than a predeterminedminimum safe level, and to vent the interior of the relief valve bellowsto vacuum or other relatively low environmental pressure when the tankpressure exceeds the predetermined minimum. To this end, the pilot valveincludes a body 134 having a control pressure compartment 136 withinwhich there is mounted an accordion member 137.' A stem 138 projectsfrom the accordion member 137 into a pilot chamber 139 provided in thevalve body and a valve closure member 141 is secured to the end of thestem. With the accordion member 137 in expanded condition, the member141 is in sealed engagement with an outlet port 142 communicating withthe pilot chamber at a position of alignment with the stem 138, asindicated in FIG- URE 12. When the accordion member 137 is in contracted"condition, however, the closure member 141 is disengaged from theoutlet port 142 as shown in FIGURE 13. In addition, the closure member141 is disposed in closed sealing relation to the interior of a bellows143 which is mounted within the pilot chamber 139 and communicated withthe control pressure chamber 136, when the accordion member 137 is inthe contracted position of FIGURE 13. However, when the accordion member137 is expanded, the interior of the bellows 143 is ported to the pilotchamher 139, as indicated in FIGURE 12. An inlet port 144 iscommunicated with the control pressure chamber 136 to facilitatecommunicable connection thereof to the tank. A pilot port 146 isprovided in communication with the pilot chamber 139 and is connected tothe interior of the relief valve bellows 131. The accordion member 137is adjusted such that when the tank pressure applied to the controlpressure chamber 136 through the port 144 is greater than apredetermined safe minimum, the accordion member is contracted and theclosure member 141 is disengaged from the port 142 and disposed insealed closing relation to the interior of the bellows 143 as shown inFIGURE 13'. Thus, the interior of the relief valve bellows 131 is portedthrough the pilot port 146 to the pilot chamber 139 and this chamber isported through outlet port 142 to a vent pipe 147 which communicateswith the vent 123 as best shown in FIGURE 7. The interior of the reliefvalve bellows is thus at this time ported to vacuum or other lowpressure and the pressure of the gas within the chamber 127 of therelief valve hence contracts the bellows to disengage the plug 132 fromthe seat 129,

thereby establishing flow of gas to the turbine nozzles 108 and 111. Theturbine 112 is thus driven and the apparatus is rendered operable toproduce its liquid-gas separating and gas venting functions. When thetank pressure is below the predetermined safe minimum, this pressureacting in chamber 136 upon accordion member 137 is insufficient tocontract same and, accordingly, the accordion member is in expandedposition as indicated in FIGURE 12. The closure member 141 is thereforein sealed closing engagement with the outlet port 142 and is disengagedfrom th bellows member 143 whereby the pilot chamber 139 is communicatedwith the chamber 136. Tank pressure consequently exists in the pilotchamber 139 and is applied through the pilot port 146 to the interior ofthe relief valve bellows 131. The pressure of the gas in the reliefvalve chamber 127 acting on the exterior of the bellows 131 isinsufficientto contract same against the tank pressure existing in itsinterior. Accordingly, the relief valve bellows 131 is in expandedposition to sealably engage the plug 132 with the seat 129 and preventflow of gas to the turbine nozzles 108 and 111. Thus, the appara-' tusis rendered inoperable in the conduct of its separating and gas ventingfunctions.

Considering now the shut-off valve 124 in greater detail, it is to benoted that this valve includes a housing 148 which is communicated atits upper end with the chamber 114 and communicated at its lower endwith the vent 123 through a port including a valve seat 149 facing intothe vent. The shut-off valve includes a bellow 151 which is mountedwithin the housing 148 and has a stem 152 1. 1 projecting therefrom witha plug 153 at its end. Th plug is disposed within the vent 123 and isengageable with the seat 149. A spring 154 disposed within the vent actsupon the plug to normally urge same into sealing engagement with theseat and to normally maintain the bellows 151 in a contracted condition.

To provide selective opening and closing of the shutoff valve 124, thevalving arragnement of the embodiment of FIGURES 7-9 is further providedwith a control valve 156 which is arranged to selectively control thepressure -within the interior of the bellows 151 between a level whichis overbalanced by the force of the spring 154, and a level whichoverbalances the spring. More particularly, with the interior pressureof the bellows 151 relatively low, the force of the spring 154 opposingthis pressure is sutiiciently large to urge the plug 153 into sealedengagement with the seat 149. With a relatively high pressure existingwithin the bellows interior, this pressure opposes and overbalances theforce of the spring 154 to thus eifect expansion of the bellows andmovement of the plug out of engagement with the seat, thereby portingthe interior of the housing 148 to the vent 123. Preferably, the controlvalve 156 is of the solenoid actuated variety and includes a valve body157 having a cylinder bore 158 with a piston 159 mounted for solenoidactuated reciprocation therein. A stem 161 projects from the piston intoa chamber 162 and also extends through a passage 163, in spaced relationto the walls thereof, into a chamber 164 communicated with the chamber162 through the passage. Valve seats 166 and 167 are provided at theopposite ends of the passage 163 which respectively face into thechamber 162 and the chamber 164. Plugs 16S and 169 are carried by thestem 161 and are respectively engageable with the seats 166 and 167. Inone solenoid actuated position of reciprocation of the piston 159 asdetermined by appropriate energization of solenoids 171 and 172 carriedby the body 157, plug 168 is in engagement with seat 166 while plug 169is disengaged from seat 167, as depicted in FIGURE 10. In anotherposition of reciprocation of the piston, plug 168 is disengaged fromseat 166 while plug 169 is engaged with seat 167, as depicted in FIGURE11. The chamber 162 is provided with an inlet port 173 which is arrangedfor communicable connection to the tank, and the chamber 164 is providedwith an outlet port 174 which is coupled by means of a vent pipe 176into communication with the vent 123. The control valve is furtherprovided with a control port 177 which is communicated with theintermediate region of the passage 163 and is communicated with theinterior of the shutoff valve bellows 151. Thus, with the control valveactuated to the position indicated in FIGURE 10, the chamber 162 isblocked from passage 163 while the interior of the shut-off valvebellows is communicated through pilot port 177, passage 163, chamber164, outlet port 174, and vent pipe 176, with the vent 123. The interiorof the shut-off valve bellows is accordingly ported to vacuum or otherlow environmental pressure such that the bellows is contracted by theforce of the spring 154 and the plug 153 is engaged with the seat 149 tothereby block communication between the chamber 114 and the vent 123.Gas flow through the apparatus is accordingly prevented irrespective ofthe condition of the pilot valve 133 as depicted in either of FIGURES l2and 13. The apparatus is, accordingly, locked in an inactive state. Withthe piston 159 of the control valve actuated to the position depicted inFIGURE 11, however, the chamber 164 is blocked from communication withthe passage 163, and tank pressure is applied through the inlet port173, chamber 162, passage 163, and control port 177 to the interior ofthe shut-off valve bellows 131. The tank pressure at the interior of thebellows is sufficient to overbalance the force of the spring 154 tothereby disengage the plug 153 from the seat 149 and thereby communicatethe chamber 114 with the vent 123. In this condition of the controlvalve, operation of the apparatus is controlled by the pilot valve 133in accordance with the pressure existing within the tank in the mannerpreviously described. More particularly, where the tank pressure isexcessive, the pilot valve 133 effects opening of the relief valve 107to thereby actuate the apparatus for gas-liquid separating and gasventing service. Where the tank pressure is not excessive, the pilotvalve effects closure of the relief valve to thereby render theapparatus inactive.

Although the present invention has been described hereinbefore withrespect to several preferred embodiments, it will be appreciated thatvarious variations and modifications may be made therein withoutdeparting from the true spirit and scope of the invention, and thus itis not intended to limit the invention except by the terms of thefollowing claims.

What is claimed is:

1. A zero gravity separator comprising an annular heat exchanger adaptedfor mounting within the upper regions of a tank containing a fluid indouble-phase liquid and gas condition, said heat exchanger having liquidflow passages extending radially therethrough, said heat exchangerhaving gas flow passages extending longitudinally thereof in heatexchange relation to said liquid flow passages and terminating in a ventpipe adapted for porting exteriorly of said tank, a turbine housingsecured to said heat exchanger and having a sealed chamber therein, aturbine journaled for rotation within said chamber, a separator disccoaxially disposed within said heat exchanger, said disc having aplurality of gas inlets extending radially thereof, a shaft coaxiallyconnecting said disc and said turbine, said shaft having a longitudinalpassage communicating with the gas inlets of said disc and having aradially extending outlet spaced therefrom, means defining a reliefvalve body in association with said turbine housings, said valve bodyhaving a flow path extending therethrough including a valve seat, nozzlemeans disposed within said turbine housing in communication with one endof said flow path through said valve body for directing gas therefrominto motivating relation to said turbine, means defining a flow path insealed rotation permitting relation to said shaft and communicating saidoutlet of the shaft passage with the second end of said flow paththrough said valve body, a pressure sensitive valve member mountedwithin said valve body and engageable with said seat, said valve membermovable between a position in engagement with said seat and a secondposition out of engagement therewith in response to gas pressures insaid tank respectively less than and greater than a predeterminedpressure, and means communicating the turbine chamber with said gaspassages of said heat exchanger.

2. A zero gravity separator comprising a turbine housing having a sealedchamber therein, a pair of turbines journaled in said chamber forindependent coaxial rota tion in opposite directions, first nozzle meansdisposed within said chamber for directing gas upon said first turbineto effect rotation thereof, second nozzle means disposed within saidchamber for directing gas upon said second turbine to effect rotationthereof,-means within said chamber defining a first orificelongitudinally intermedate said first and second turbines in alignmentwith said first nozzle means to receive gas directed therefromsubsequent to driving of said first turbine and direct the gas indriving relation to said second turbine, means defining a second orificelongitudinally intermediate said first and second turbines in alignedrelation with said second nozzle means-for receiving gas directedtherefrom subsequent to driving of said second turbine and directing thegas into driving relation to said first turbine, first and secondannular heat exchangers secured to said turbine housing respectively incoaxially outwardly spaced relation to said first and second turbines,said first and second heat exchangers each having liquid flow passagesextending radially therethrough and gas fiow passages extendinglongitudinally thereof in heat exchange relation with said liquid fiowpassages, first and second separator discs respectively coaxiallymounted for rotation within said first and second heat exchangers, saidfirst and second discs respectively having radially extending gasinlets, first and second shafts respectively coaxially connecting saidfirst disc and said first turbine and said second disc and said secondturbine, said first and second shafts respectively having longitudinalpassages communicating with the gas inlets of said first and seconddiscs and having gas outlets intermediate said first disc and firstturbine and intermedate said second disc and said second turbine, meansdefining a first flow passage in sealed rotation permitting relation tosaid first shaft and communicating the outlet thereof with said firstnozzle means, means defining a second flow path in sealed rotationpermitting relation to said second shaft and communicating the outletthereof with said second nozzle means, a third flow path communicating aregion of said chamber adjacent said second turbine and said firstorifice with said gas passages of said second heat exchanger, a fourthflow path communicating a region of said chamber adjacent said firstturbine and said second orifice with said gas passages of said firstheat exchanger, and means communicating the gas passages of said firstand second heat exchangers with an outlet vent.

3. A zero gravity separator according to claim 2, wherein said first andsecond turbines are journaled in bearings within said chamber and meansdefining flow paths between said first and second orifices and saidbearings for gas cooling the latter.

4. A zero gravity separator according to claim 2, further defined by afirst relief valve body carried by said turbine housing and including avalve chamber and inlet and outlet passages communicating said firstflow path and first nozzle means through said chamber, said outletpassage of said valve body including a valve seat, an accordion valvemember mounted within said valve chamber for expansive and contractivemovement into and out of engagement with said seat, a second reliefvalve body carried by said turbine housing having a sealedchamber andinlet and outlet passages communicat ing said second flow path and saidsecond nozzle means through said chamber, said outlet passages of saidsecond valve body havinga valve seat, asecond accordion valve membermounted within said chamber of said second valve body for expansive andcontractive. movement into and out of'engagement with said seat of saidoutlet passage thereof, and pilot valve means coupled to the interiorsof said first and second accordion valve members for selectivelycontrolling the pressures therein between levels greater than and lessthan the pressure of gas in the chambers of said first and second valvebodies.

5. A zero gravity separator according to claim 4, further defined bysaid turbine housing and said first and second heat exchangers beingcontained within a closed tank and said outlet vent being portedexteriorly of said tank, and by said pilot valve means communicating theinteriors of said first and second accordion valve members with saidoutlet vent and the interior of said tank respectively in response topressures in said tank greater than and less than apredeterminedpressure.

6. A zero gravity separator according to claim 5, further defined by acontrol valve body having a pilot chamber and a control pressure chambercommunicated through a leak passage, said control valve body having apilot port communicating with said pilot chamber and coupled to theinteriors of the first and second accordion valve members in thechambers of said first and second relief valve bodies, said controlvalve body having an outlet passage communicating said pilot chamberwith said outlet vent and a valve seat in the pilot chamber at theentrance of said outlet passage, said control valve body having an inletport communicating said control pressure chamber with the interior ofsaid tank, a pressure sensing accordion member mounted in said controlpressure chamber, a closure member connected to said pressure sensingaccordion member and disposed in said pilot chamber for engagement withsaid seat therein, said pressure sensing accordion member movablebetween first and second positions wherein said closure member isengaged with and disengaged from the seat in said pilot chamberrespectively in response to pressures in said control pressure chamberless than and greater than said predetermined pressure, said pilotchamber, said control pressure chamber, said outlet passage, said pilotport, said inlet port, and said accordion member with closure memberconnected thereto thereby comprising said pilot valve means, saidcontrol valve body having an outlet chamber communicated with saidoutlet vent and an inlet passage communicating the gas passages of saidfirst and second heat exchangers with said outlet chamber, said outletchamber having a valve seat at the termination of said inlet passagetherein, a solenoid actuatable piston mounted for reciprocation in saidcontrol valve body and having a closure member connected theretorespectively engaged with and disengaged from said seat in said outletchamber in response to reciprocation of said piston between first andsecond positions, and solenoid means for selectively reciprocating saidpiston between said first and second positions.

7. A zero gravity separator comprising an elongated hollow cylindricalheat exchanger adapted for mounting within the upper regions of a tankcontaining a fluid in double-phase liquid and gas condition, said heatexchanger having a plurality of longitudinally extending gas flowpassages with the passages of one semicircular half sector of the heatexchanger communicated at one end with the passages of the other halfsector of the heat exchanger to thereby circulate gases in onelongitudinal direction through the first half sector of the heatexchanger and then in the opposite longitudinal direction through thesecond half sector of the heat exchanger, said heat exchanger havingliquid flow passages extending radially therethrough, a hollow shaftjournaled for rotation coaxially within said heat exchanger with one endof the shaft being closed and the other end being opened to define aflow path longitudinally therethrough, said shaft having a plurality oflongitudinally spaced outwardly extending vanes encompassing radial gasinlets communicated with said flow path, said shaft upon rotationpropelling liquid introduced to the hollow interior of said heatexchanger from said tank outwardly through said liquid flow passages forreturn to said tank and channeling gas introduced to the hollow interiorof the heat exchanger through said gas inlets of said shaft to the flowpath extending longitudinally thereof, a turbine coaxially connected indriving relation to said shaft to effect said rotation thereof, meanscommunicating with said flow path of said shaft for directing gastherefrom into motivating relation to said turbine, said gas beingexpanded and cooled in motivating said turbine, means channelingexpanded gas from said turbine to said gas passages of the first halfsector of said heat exchanger, and means for venting the gas passages ofthe second half sector of said heat exchanger exteriorly of said tank.

8. A zero gravity separator according to claim 7 further defined bymagnetic friction clutch means coupling said turbine to said shaft, andmeans for channeling gas from the gas passages of said second halfsector of said heat exchanger into cooling relation to said clutch meansprior to venting of said gas.

9. A zero gravity separator according to claim 7, further defined by arelief valve communicating said flow path of said shaft with saidturbine, said relief valve including an accordion valve member forblocking communication between the flow path and turbine in response toexpansion of the member and establishing communication between said flowpath of said shaft and said turbine in response to contraction of theaccordion member; and a pilot valve including a pilot port connected tothe interior of said accordion member of said relief valve, said pilotvalve having an outlet port communicated with said vent and an inletport adapted for communication with said tank, said pilot valve operableto communicate the inlet and pilot ports thereof in response topressures at the inlet port less than a predetermined pressure and tocommunicate the outlet and pilot ports thereof in response to pressuresat the inlet port greater than said predetermined pressure.

10. A zero gravity separator according to claim 9, further defined by ashut-off valve communicating the gas flow passages of said second halfsector of said heat exchanger with said vent, said shut-off valveincluding an accordian valve member for establishing communicationbetween the gas flow passages of the second half sector of the heatexchanger and said vent upon expansion of the shut-off valve accordionmember in response to relatively high pressure in the interior thereofwhile blocking communication between the gas flow passages of the secondhalf sector of said heat exchanger and said vent upon contraction of theshut-off valve accordion member in response to relatively low pressurein the interior thereof, and control valve means for selectively portingthe interior of said shut-off valve accordion member to said tank andsaid vent respectively to thereby establish said relatively high and lowpressures therein.

11. A zero gravity separator comprising a turbine housing adapted formounting within the upper regions of a tank containing fluid indouble-phase gas and liquid condition, said turbine housing havingfirst, second and third chambers therein sealed from each other andcoaxially aligned, said housing having an inlet flow passagecommunicating with said second chamber and first and second outlet flowpassages respective-1y communicating with said first and secondchambers, a turbine journaled for rotation coaxially within said firstchamber, first and second turbine nozzles disposed at diametricallyopposed positions of said first chamber adjacent said turbine, a hollowelongated cylindrical heat exchanger coaxially secured to said turbinehousing adjacent said third chamber thereof, said heat exchanger havinglongitudinal gas passages with the gas passages of a first semicircularhalf of the heat exchanger communicating at a first end thereof withsaid first outlet passage of said turbine housing and the gas passagesof the second semicircular half of the heat exchanger communicating atthe first end thereof with said inlet passage of said turbine housing,said gas passages of said first half of said heat exchanger communicatedwith the gas passages of said second half of said heat exchanger at thesecond ends thereof, said heat exchanger having liquid passagesextending radially therethrough in heat exchange relation with said gaspassages, a hollow shaft coaxially disposed within the hollow interiorof said heat exchanger and journaled for rotation between the oppositeends thereof, said shaft closed at the second end of heat exchanger andcommunicating at the first end of said heat exchanger with said thirdchamber of said turbine housing, said shaft having a plurality oflongitudinally spaced outwardly extending vanes encompassing radial gasinlets communicating with the hollow shaft interior, said shaft uponrotation thereby propelling liquid outwardly through said liquidpassages of said heat exchanger and channeling gas into said gas inletsto the hollow shaft interior for passage to the third chamber of saidturbine housing, a magnetic friction clutch disposed within said secondchamber of said turbine housing and coaxially coupling said turbine tosaid shaft, and a vent adapted for positioning exteriorly of said tankand communicably connected to said second outlet passage of said turbinehousing, said turbine housing having a flow path communicating saidthird chamber and said turbine nozzles, whereby fluid entering thehollow interior of said heat exchanger is separated by said shaft withthe liquid being propelled outwardly through the liquid passages of saidheat exchanger and the gas being channeled through the hollow interiorof said shaft to said third chamber of said turbine housing, said gas isdirected from said third chamber to said turbine nozzles and emanatestherefrom to drive said turbine which in turn effects rotation of saidshaft while the gas expands and is cooled in driving said turbine, thecooled gas is directed from the first chamber of said turbine housingthrough the gas passages of said heat exchanger to thereby cool theliquid directed through the liquid passages thereof, the gas is directedfrom the gas passages of the heat exchanger to the second chamber ofsaid turbine housing to therein cool said clutch, and is directed fromthe second chamber to said vent for porting exteriorly of said tank.

12. A zero gravity separator according to claim 11, further defined by arelief valve body carried by said turbine housing and having a reliefvalve chamber with communicating inlet and outlet passages, said outletpassage of said relief valve body having a valve seat, said inlet andoutlet passages of said relief valve body respectively communicated withsaid third chamber of said turbine housing and said turbine nozzle, anaccordion valve member mounted within said relief valve chamber andexpansively movable into engagement with said seat and contractiblymovable out of engagement therewith, a pilot valve body carried by saidturbine housing having a pilot chamber and a control pressure chamber,said pilot valve body having an outlet port communicating said pilotvalve chamber with said vent and a pilot port communicating the pilotvalve chamber with the interior of the accordion valve member disposedin said relief valve chamber, said pilot valve body having an inlet portfor communicating said control pressure chamber with said tank,accordion valve means mounted within said control pressure chamber formovement between a first position wherein said control pressure chamberis communicated with said pilot chamber and said outlet port is closedand a second position wherein communication between said controlpressure chamber and said pilot chamber is blocked and said outlet portis open, said accordion valve means movable to said first position inresponse to pressures in said control pressure chamber less than apredetermined pressure and movable to said second position in responseto pressures in said control pressure chamber in excess of saidpredetermined pressure, a shut-off valve body carried by said turbinehousing having a shut-off valve chamber with an inlet passagecommunicating with said second chamber of said turbine housing and anoutlet passage communicating with said vent, said outlet passage of saidshut-off valve housing including a seat, an accordion valve memberdisposed within said shut-off valve chamber for contractive movementinto engagement with said seat and expansive movement out of engagementtherewith, a control valve body carried by said turbine housing havingan inlet port, an outlet port, and a pilot port, said inlet port of saidcontrol valve body adapted for communication with said tank, said outletport of said control valve body communicated with said vent, and saidpilot port of said control valve body communicated with the interior ofthe accordion member disposed within said shut-off valve chamber, asolenoid actuatable piston with-in said control valve body movablebetween a first position establishing communication between said pilotport and said outlet port and a second position establishingcommunication between said pilot port and said inlet port, and solenoidmeans associated with said control valve body for selectively actuatingsaid piston.

13. A zero gravity separator comprising hollow cylindrical heatexchanger means adapted for mounting within the upper regions of a tankcontaining a fluid in doublephase liquid and gas condition, said heatexchanger means having liquid flow passages extending radiallytherethrough, said heat exchanger means having gas flow passagesextending longitudinally thereof in heat exchange relation to saidliquid flow passages and communicating with a vent for dispositionexteriorly of said 1 7 tank; separator means including at least oneseparator element mounted for rotation coaxial-1y Within said heatexchanger means, each separator element being adapted to propel liquidintroduced from said tank to the hollow interior of said heat exchangermeans radially outward through said liquid flow passages in response torotation of the element, each separator element having circumferentiallydisposed gas inlets extending inwardly into communication with a commongas flow pathfor receiving gas introduced from said tank to the hollowinterior of said heat exchanger means; a turbine connected in drivingrelation to each separator element to effect said rotation thereof; flowmeans communicating with said flow path of each separator element fordirecting gas therefrom into motivating relation to said turbineconnected thereto, said gas being expanded and cooled in motivating saidturbine; valve means in operable relation to said flow means forpermitting flow the-rethrough in response to pressures in said tank inexcess of a predetermined pressure and blocking flow through the flowmeans in response to pressures in said tank less than said predeterminedpressure; and means for channeling expanded gas from said turbine tosaid gas passages of said 18 heat exchanger means, said gas therebycooling said liquid returned to the tank through the liquid passages ofsaid heat exchanger means prior to venting of the gas exteriorly of thetank.

14. A zero gravity separator according to claim 13, further defined bysaid valve means including control means for selectively opening andclosing communication between said gas passages of said heat exchangermeans and said vent.

References Cited by the Examiner UNITED STATES PATENTS 2,216,939 10/1940Dodge 55184 2,595,384 5/1'952 Dunmire 55195 X 2,952,329 9/1960Cunningham et al. 55-199 2,952,330 9/1960 WinslOW 55202 3,021,682 2/1962Baker et al. 55-l95 3,107,988 10/1963 Taylor et al. 55-404 REUBENFRIEDMAN, Primary Examiner.

J. ADEE, Assistant Examiner.

13. A ZERO GRAVITY SEPARATOR COMPRISING HOLLOW CYLINDRICAL HEATEXCHANGER MEANS ADAPTED FOR MOUNTING WITHIN THE UPPER REGIONS OF A TANKCONTAINING A FLUID IN DOUBLEPHASE LIQUID AND GAS CONDITION, SAID HEATEXCHANGER MEANS HAVING LIQUID FLOW PASSAGES EXTENDING RADIALLYTHERETHROUGH, SAID HEAT EXCHANGER MEANS HAVING GAS FLOW PASSAGESEXTENDING LONGITUDINALLY THEREOF IN HEAT EXCHANGE RELATION TO SAIDLIQUID FLOW PASSAGES AND COMMUNICATING WITH A VENT FOR DISPOSITIONEXTERIORLY OF SAID TANK; SEPARATOR MEANS INCLUDING AT LEAST AT LEAST ONESEPARATOR ELEMENT MOUNTD FOR ROTATION COAXIALLY WITHIN SAID HEATEXCHANGER MEANS, EACH SEPARATOR ELEMENT BEING ADAPTED TO PROPEL LIQUIDINTRODUCED FROM SAID TANK TO THE HOLLOW INTERIOR OF SAID HEAT EXCHANGERMEANS RADIALLY OUTWARD THROUGH SAID LIQUID FLOW PASSAGES IN RESPONSE TOROTATION OF THE ELEMENT, EACH SEPARATOR ELEMENT HAVING CIRCUMFERENTIALLYDISPOSED GAS INLETS EXTENDING INWARDLY INTO COMMUNICATION WITH A COMMONGAS FLOW PATH FOR RECEIVING GAS INTRODUCED FROM SAID TANK TO THE HOLLOWINTERIOR OF SAID HEAT EXCHANGER MEANS; A TURBINE CONNECTED IN DRIVINGRELATION TO EACH SEPARATOR ELEMENT TO EFFECT SAID ROTATION THEREOF; FLOWMEANS COMMUNICATING WITH SAID FLOW PATH OF EACH SEPARATOR ELEMENT FORDIRECTING GAS THEREFROM INTO MOTIVATING RELATION TO SAID TURBINECONNECTED THERETO, SAID GAS BEING EXPANDED AND COOLED IN MOTIVATING SAIDTURBINE; VALVE MEANS IN OPERABLE RELATION TO SAID FLOW MEANS FORPERMITTING FLOW THERETHROUGH IN RESPONSE TO PRESSURE IN SAID TANK INEXCESS OF A PREDERTERMINED PRESSURE AND BLOCKING FLOW THROUGH THE FLOWMEANS IN RESPONSE TO PRESSUDRE IN SAID TANK LESS THAN SAID PREDETERMINEDPRESSURE; AND MEANS FOR CHANNELING EXPANDED GAS FROM SAID TURBINE TOSAID GAS PASSAGES OF SAID HEAT EXCHANGER MEANS, SAID GAS THEREBY COOLINGSAID LIQUID RETURNED TO THE TANK THROUGH THE LIQUID PASSAGES OF SAIDHEAT EXCHANGER MEANS PRIOR TO VENTING OF THE GAS EXTERIORLY OF THE TANK.